An adjustable tail nozzle mechanism for a micro turbojet engine

Abstract

This utility model relates to an adjustable tail nozzle mechanism for a micro turbojet engine, belonging to the technical field of tail nozzle structures for micro turbojet engines. It includes opposing adjusting plates and opposing fixed plates. Each adjusting plate has an adjusting shaft on its outer upper surface and a fixedly connected root rotating shaft at its lower surface. Both ends of the root rotating shaft penetrate the fixed plate and are detachably connected to it. Each adjusting shaft has a connecting control rod at both ends. The other end of the control rod on the same side has a ball joint connector on its outer surface and a guide rail bracket on its inner surface, with guide rails mounted on the guide rail bracket. This invention distributes stress by having forces applied to both ends of the two adjusting plates, effectively avoiding the risk of fatigue cracks at the root of the rotating shaft and improving its service life. The support rods provide limiting protection during the adjustment plate's movement. The structure is simple and performs well.

Description

Technical Field

[0001] This utility model relates to an adjustable tail nozzle mechanism for a micro turbojet engine, belonging to the technical field of tail nozzle structure for micro turbojet engines. Background Technology

[0002] Traditional micro turbojet engines typically employ a simple convergent nozzle structure, i.e., a fixed nozzle. While this design is structurally simple, its fixed nozzle area prevents dynamic adjustment based on specific flight conditions, resulting in performance limitations under certain conditions and low gas expansion efficiency, leading to thrust loss and waste.

[0003] Most existing adjustable nozzles are used in turbojet engines with large thrust. Their complex structure and numerous parts make miniaturization difficult. Some two-dimensional adjustable nozzles used in micro turbojet engines open and close the adjustment plate by rotating the shaft of the adjustment plate. This structure is labor-intensive, inefficient, and suffers from stress concentration. Under some extreme conditions, the convergence action may not be complete, and there is a risk of fatigue failure after long-term use. Therefore, it is necessary to develop an adjustable nozzle mechanism for micro turbojet engines. Utility Model Content

[0004] This invention addresses the shortcomings of the prior art by providing an adjustable tailjet mechanism for a micro turbojet engine.

[0005] The technical solution of this utility model to solve the above-mentioned technical problems is as follows: An adjustable tail nozzle mechanism for a micro turbojet engine includes an adjusting plate and a fixed plate arranged opposite each other. The upper outer side of each adjusting plate is provided with an adjusting shaft, and the lower end of each adjusting plate is provided with a root rotating shaft fixedly connected thereto. Both ends of the root rotating shaft pass through the fixed plate and are detachably connected to the fixed plate. Both ends of each adjusting shaft are provided with connected control rods. The other end of the control rod on the same side is provided with a ball joint connector on the outer side and a guide rail bracket on the inner side. The guide rail bracket is provided with a guide rail. The ball joint connector, the two control rods on the same side away from the adjusting shaft end, and the guide rail are connected in sequence by pins. The lower end of each ball joint connector is provided with a pull rod connected to a power source.

[0006] Furthermore, connecting struts are provided between the outer sides of the fixing plates.

[0007] Furthermore, the angular range of motion of the control linkage on the same side is 42° to 102°.

[0008] Furthermore, both ends of the root shaft are provided with detachable plugs, and a shaft fixing plate is provided between the plug and the fixing plate.

[0009] Furthermore, the upper end of the root shaft is provided with a groove for connecting with the adjustment plate.

[0010] Furthermore, a thermocouple mounting bracket is provided at the center of the upper end of the outer side of the fixing plate, and the thermocouple mounting bracket is located between the two control linkages.

[0011] Furthermore, the outer side of the adjustment plate is provided with several reinforcing ribs.

[0012] Furthermore, the lower end of the adjusting plate and the fixing plate is provided with a base plate, and the base plate is provided with a tail nozzle.

[0013] Furthermore, the top of the adjusting plate is higher than the top of the fixed plate.

[0014] Compared with the prior art, the beneficial effects of this utility model are: This invention employs a distributed linkage structure, eliminating the traditional shaft-driven transmission structure and transferring the force point from the shaft to the end of the adjusting plate. This makes the force on the adjusting plate more direct, the entire structure less strenuous, and avoids the possibility of failure to close properly when driven from the shaft. Furthermore, it avoids the stress concentration caused by the exhaust jet impact on the adjusting plate, which could lead to fatigue fracture over time if driven from the shaft. By distributing the force on both sides of the two adjusting plates' ends, the structure effectively mitigates the risk of fatigue cracks at the root of the shaft, thus improving service life. The addition of support rods provides limiting protection during the adjusting plate's movement. The structure is simple and performs well. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0016] Figure 2 This is a schematic diagram of the rear structure of this utility model.

[0017] Figure 3 This is a top view of the structure of this utility model.

[0018] In the diagram, 1. Adjusting plate; 11. Adjusting shaft; 12. Reinforcing rib; 13. Root shaft; 14. Shaft fixing plate; 15. Shaft support plate; 2. Fixing plate; 21. Support rod; 3. Control linkage; 31. Pin; 4. Ball head connector; 5. Pull rod; 6. Guide rail bracket; 61. Guide rail; 7. Thermocouple fixing bracket. Detailed Implementation

[0019] The principles and features of this utility model are described below with reference to the accompanying drawings. The examples given are only for explaining this utility model and are not intended to limit the scope of this utility model.

[0020] like Figures 1-3As shown, the adjustable tail nozzle mechanism for a micro turbojet engine in this embodiment includes an adjusting plate 1 and a fixed plate 2 arranged opposite to each other. The upper outer side of the adjusting plate 1 is provided with an adjusting shaft 11, and the lower end is provided with a root rotating shaft 13 fixedly connected. Both ends of the root rotating shaft 13 pass through the fixed plate 2 and are detachably connected to the fixed plate 2. Both ends of the adjusting shaft 11 are provided with control rods 3. The other side of the control rod 3 on the same side is provided with a ball connector 4 on the outer side and a guide rail bracket 6 on the inner side. The guide rail bracket 6 is provided with a guide rail 61. The ball connector 4, the two control rods 3 on the same side away from the adjusting shaft 11, and the guide rail 61 are connected in sequence by pins 31. The lower end of the ball connector 4 is provided with a pull rod 5 connected to the power source.

[0021] A connecting strut 21 is provided between the outer sides of the fixing plate 2.

[0022] The angular range of motion of the control linkage 3 on the same side is 42° to 102°.

[0023] The rotating shaft support plate 15 is T-shaped.

[0024] Both ends of the root shaft 13 are provided with detachable plugs, and a shaft fixing piece 14 is provided between the plug and the fixing plate 2.

[0025] The upper end of the root shaft 13 is provided with a groove for connecting to the adjusting plate 1.

[0026] A thermocouple mounting bracket 7 is located at the center of the upper part of the outer side of the fixing plate 2, between the two control linkages 3. A temperature-measuring thermocouple is installed inside the thermocouple mounting bracket 7.

[0027] The outer side of the adjustment plate 1 is provided with several reinforcing ribs 12.

[0028] The lower ends of the adjusting plate 1 and the fixing plate 2 are provided with a base plate, and the base plate is provided with a tail nozzle.

[0029] The top of the adjusting plate 1 is higher than the top of the fixed plate 2.

[0030] The connection ends of the two control links 3 on the same side and the ball connector 4 are stepped and mutually cooperate. The total thickness of the connection between the two control links 3 and the ball connector 4 is the same as the thickness of a single control link 3.

[0031] During operation, the lever 5 is driven and controlled by a power source such as a motor or cylinder to reciprocate. At this time, the lower end of the control rod 3 on the adjustment plate is constrained by the guide rail 6 to reciprocate linearly. The control rod 3 at the upper end of the adjustment plate transmits the pulling or pushing force, which drives the two opposing adjustment plates 1 to rotate around the root shaft 13, controlling the two adjustment plates 1 to open or close, and finally realizing the adjustment of the tail nozzle area; the temperature is measured by the thermocouple in the thermocouple fixing bracket 7.

[0032] This invention employs a distributed linkage structure, eliminating the traditional shaft-driven transmission structure. The force point is transferred from the shaft to the end of the adjusting plate 1, making the force on the adjusting plate 1 more direct and the entire structure more labor-saving. This avoids the possibility of failure to close properly when the transmission is from the shaft. Furthermore, it avoids the stress concentration caused by the exhaust jet impact on the adjusting plate 1, which could lead to fatigue fracture over time if the transmission were from the shaft. This invention distributes the force by having the two adjusting plates 1 bear force on opposite sides at their ends, effectively mitigating the risk of fatigue cracks at the root of the shaft 13 and improving service life. The support rod 21 provides limiting protection during the movement of the adjusting plate 1. The structure is simple and performs well.

[0033] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. An adjustable nozzle for a micro turbojet engine comprising a pair of opposite adjustment plates (1) and a pair of opposite fixed plates (2), characterized in that: The upper outer side of the adjustment plate (1) is provided with an adjustment shaft (11), and the lower end is provided with a root rotating shaft (13) that is fixedly connected. Both ends of the root rotating shaft (13) pass through the fixed plate (2) and are detachably connected to the fixed plate (2). Both ends of the adjustment shaft (11) are provided with control rods (3). The other end of the control rod (3) on the same side is provided with a ball connector (4) on the outer side and a guide rail bracket (6) on the inner side. The guide rail bracket (6) is provided with a guide rail (61). The ball connector (4), the two control rods (3) on the same side away from the adjustment shaft (11), and the guide rail (61) are connected in sequence by pins (31). The lower end of the ball connector (4) is provided with a pull rod (5) that is connected to the power source.

2. The adjustable nozzle mechanism for a micro turbojet engine according to claim 1, characterized in that: A connecting strut (21) is provided between the outer sides of the fixing plate (2).

3. Adjustable nozzle for micro turbojet engines according to claim 1 or 2, characterized in that: The angular range of the control linkage (3) on the same side is 42° to 102°.

4. The adjustable nozzle mechanism for a micro turbojet engine of claim 1, wherein: Both ends of the root shaft (13) are provided with detachable plugs, and a shaft fixing piece (14) is provided between the plug and the fixing plate (2).

5. The adjustable nozzle mechanism for micro turbojet engines according to claim 1, characterized in that: The upper end of the root shaft (13) is provided with a groove for connecting with the adjusting plate (1).

6. The adjustable nozzle mechanism for a micro turbojet engine of claim 1, wherein: Thermocouple mounting bracket (7) is provided at the center of the upper part of the outer side of the mounting plate (2), and the thermocouple mounting bracket (7) is located between the two control rods (3).

7. The adjustable nozzle mechanism for micro turbojet engines according to claim 1, characterized in that: The outer side of the adjustment plate (1) is provided with several reinforcing ribs (12).

8. The adjustable nozzle mechanism for a micro turbojet engine of claim 1, wherein: The lower ends of the adjusting plate (1) and the fixing plate (2) are provided with a base plate, and the base plate is provided with a tail nozzle.

9. The adjustable nozzle mechanism for micro turbojet engines according to claim 1, characterized in that: The top of the adjusting plate (1) is higher than the top of the fixed plate (2).

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